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A GENERATOR CONTROL UNIT (GCU), USED TO MONITOR AND CONTROL THE INTEGRATED DRIVE GENERATORS WHEN THEY ARE POWERING AIRCRAFT LOAD BUSES. IT HAS TWO MAIN AIRCRAFT TASKS: CONTROL AND PROTECTION; TO MONITOR AND CONTROL THE QUALITY OF ELECTRIC POWER SUPPLIED TO THE AIRCRAFT AND BUILT-IN TEST EQUIPMENT (BITE); TO COLLECT AND ANALYSE FAULT DATA AND SAVE THIS FOR LATER RETRIEVAL BY MAINTENANCE PERSONNEL.

PROBE HEAT COMPUTER (PHC), USED IN CONJUNCTION WITH AN AIRCRAFT ANTI-ICING SYSTEM OF PROBES AND SENSORS. THE PHC IS A RECTANGULAR UNIT WHICH HAS A BOX ASSEMBLY WITH PRINTED CIRCUIT BOARDS. THE CPU PERMANENTLY MONITORS THE PROBE ANTI-ICING OPERATION. THE PHC PROVIDES AN ANTI-ICING FUNCTION WITH DATA PROCESSING. THE FUNCTIONS INCLUDE: POWER SUPPLY, ANTI ICING OF THE TOTAL PRESSURE PROBE, OUTER AIR TEMPERATURE SENSOR, ANGLE OF ATTACK SENSOR AND RIGHT/LEFT STATIC PRESSURE PROBE. IT PROVIDES POWER SUPPLY CONTROL AND SUPPLIES RELATED WARNING SIGNALS.

A HYDROMECHANICAL UNIT (HMU), A COMPONENT OF AN AIRCRAFT ENGINE SYSTEM. THE HMU RESPONDS TO ELECTRICAL SIGNALS FROM AN EEC TO METER ENGINE FUEL FLOW AND MODULATE MOTIVE FLOW TO SIX EXTERNAL HYDRAULIC SYSTEMS. A COMPONENT IN THE HMU CAUSES SERVO POSITIONING OF THE UNIT MV. THE MV POSITION ESTABLISHES THE PROPER METERED FUEL DELIVERY ORIFICE FOR THE COMMANDED FUEL FLOW. A MECHANICAL OVERSPEED GOVERNOR SWITCH LIMITS ENGINE SPEED TO 106 PERCENT MAXIMUM.

GENERATOR CONTROL UNIT (GCU) FOR AIRBUS A340 CIVIL AIRCRAFT. THE UNIT CONSISTS OF A COMPACT CAST ALUMINIUM HOUSING CONTAINING A SERIES OF PRINTED CIRCUIT BOARDS. THE UNIT CONTROLS THE VOLTAGE COMING FROM THE GENERATOR KEEPING IT AT A CONSTANT AND PROVIDING OVER VOLTAGE PROTECTION. IT IS ALL PERFORMED ELECTRONICALLY WITH THE UNIT SENSING VARIOUS PARAMETERS AND COMPARING THEM WITH A STANDARD. IT CONTROLS THROUGH THE FIELD EXCITATION CIRCUIT WHICH MAKES ADJUSTMENTS THROUGH THE FIELD WINDING.

SWITCH ALTITUDE FOR AIRBUS A320 CIVIL AIRCRAFT. FUNCTIONAL DESCRIPTION : THE ALTITUDE SWITCH 16WR, WHICH IS INSTALLED IN THE AVIONICS COMPARTMENT, STARTS THE AUTOMATIC OPERATION OF THE PASSENGER EMERGENCY-OXYGEN SYSTEM. IF THE ALTITUDE SWITCH DOES NOT WORK YOU CAN PUSH THE 'MAN ON' PUSHBUTTON SWITCH 14WR. THE ALTITUDE SWITCH CLOSES WHEN THE CABIN PRESSURE DECREASES TO A PRESSURE EQUIVALENT TO 14000 +0 -500 ft. THIS STARTS THE EMERGENCY OXYGEN SUPPLY SYSTEM.